A Systematic Comparison of Reusable First Stage Return Options
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Open-Loop Flight Testing of COBALT GN&C Technologies for Precise Soft Landing
Open-Loop Flight Testing of COBALT GN&C Technologies for Precise Soft Landing John M. Carson III1,3,∗, Farzin Amzajerdian2,y, Carl R. Seubert3,z, Carolina I. Restrepo1,x 1NASA Johnson Space Center (JSC), 2NASA Langley Research Center (LaRC), 3Jet Propulsion Laboratory (JPL), California Institute of Technology, A terrestrial, open-loop (OL) flight test campaign of the NASA COBALT (CoOper- ative Blending of Autonomous Landing Technologies) platform was conducted onboard the Masten Xodiac suborbital rocket testbed, with support through the NASA Advanced Exploration Systems (AES), Game Changing Development (GCD), and Flight Opportuni- ties (FO) Programs. The COBALT platform integrates NASA Guidance, Navigation and Control (GN&C) sensing technologies for autonomous, precise soft landing, including the Navigation Doppler Lidar (NDL) velocity and range sensor and the Lander Vision System (LVS) Terrain Relative Navigation (TRN) system. A specialized navigation filter running onboard COBALT fuzes the NDL and LVS data in real time to produce a precise navi- gation solution that is independent of the Global Positioning System (GPS) and suitable for future, autonomous planetary landing systems. The OL campaign tested COBALT as a passive payload, with COBALT data collection and filter execution, but with the Xo- diac vehicle Guidance and Control (G&C) loops closed on a Masten GPS-based navigation solution. The OL test was performed as a risk reduction activity in preparation for an upcoming 2017 closed-loop (CL) flight campaign in which Xodiac G&C will act on the COBALT navigation solution and the GPS-based navigation will serve only as a backup monitor. I. Introduction Introduction will discuss the NASA need for Precision Landing and Hazard Avoidance (PL&HA) tech- nologies for future, prioritized solar-system destinations (robotic and human missions), as well as provide an overview for the COBALT project and how it fits within the NASA PL&HA technology development roadmap. -
On Orbital Debris JEFF FOUST, COLLEGE PARK, Md
NOVEMBER 24, 2014 SPOTLIGHT Clyde Space See page 12 www.spacenews.com VOLUME 25 ISSUE 46 $4.95 ($7.50 Non-U.S.) PROFILE/22> YVONNE PENDLETON DIRECTOR, SOLAR SYSTEM EXPLORATION RESEARCH VIRTUAL INSTITUTE INSIDE THIS ISSUE LAUNCH INDUSTRY Swift Development of Ariane 6 Urged Applauding the end of a French-German impasse over the Ariane 6 rocket, the European Satellite Operators Association said the vehicle needs to be in service as quickly as possible. See story, page 8 ATK Hints at Antares Engine Selection Alliant Techsystems Chief Executive Mark DeYoung said there are no near-term liquid- propulsion alternatives to Russian engines for U.S. rockets. See story, page 6 ESA PHOTO Virginia May Seek Federal Funds for Wallops > “We have found a compromise that is OK for both countries, for the other participating states and also for industry,” Brigitte Zypries (above), Germany’s Virginia’s two U.S. senators said they may seek federal funds to cover $20 million in repairs to the space minister, said of an agreement under which Germany and France will back the Ariane 6 rocket and scrap the Ariane 5 Midlife Evolution. Wallops Island launch pad damaged when Orbital Sciences’ Antares exploded. See story, page 6 MILITARY SPACE Protected Tactical Waveform Taking Shape German-French Compromise The U.S. Air Force is expected to demonstrate its protected tactical waveform in new modems and reworked terminals as early as 2018. See story, page 11 U.S. To Grant Indirect Access to Space Fence Paves Direct Path to Ariane 6 The Pentagon’s international space surveillance partners will have indirect access to data from the Air Force’s next-generation Space Fence tracking system. -
MT Aerospace (Germany)
https://ntrs.nasa.gov/search.jsp?R=20080014278 2019-08-30T04:19:50+00:00Z European Directions for Hypersonic Thermal Protection Systems and Hot Structures 31st Annual Conference on Composites Materials and Structures Daytona Beach, FL January 22, 2007 David E. Glass NASA Langley Research Center, Hampton, VA 23681 Approved for Public Release, Distribution Unlimited Agenda ♦ Background • Comments on prior ESA workshop • X-38 • Hopper ♦ Flight Vehicle Based Technology Development • IXV (ESA) • EXPERT (ESA) • USV (Italy) • SHEFEX (Germany) • SHyFE (UK) • LEA (France) • Foton (Russia) ♦ Non-Vehicle Specific Technology ♦ Concluding Remarks 2 European TPS and Hot Structures Research and Development ♦TPS and hot structures research and development critical for future space vehicles ♦Developing next generation TPS and hot structures technology (not Space Shuttle derived technology) ♦Long-term funding based on technology needs ♦Wide industry support and commitment to X-38 program ♦Test facilities developed for TPS and hot structures development • Thermal/structural test chamber • Arc-jet tunnels developed in recent years ♦Technology development has broad base • Fabrication • Testing • Large components • Fasteners • Bearings • Oxidation protection • Damage repair • Life cycle Wayne Sawyer comments from previous ESA TPS & Hot Structures Workshop 3 European TPS and Hot Structures Research and Development ♦ Proposing numerous experimental launch vehicles dedicated to or with TPS and hot structures research of prime consideration ♦ Committing significant -
Mission Analysis and Preliminary Re-Entry Trajectory Design of the DLR Reusability Flight Experiment Refex
8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Mission Analysis and Preliminary Re-entry Trajectory Design of the DLR Reusability Flight Experiment ReFEx Sven Stappert*, Peter Rickmers*, Waldemar Bauer*, Martin Sippel* *German Aerospace Center (DLR), Institute of Space Systems, Robert-Hooke-Straße 7, 28359 Bremen [email protected], [email protected], [email protected], [email protected] Abstract Driven by the recently increased demand for investigating reusable launchers, the German Aerospace Center (DLR) is currently developing the Reusability Flight Experiment (ReFEx). The goal is to demonstrate the capability of performing an atmospheric re-entry, representative of a possible future winged reusable stage, and to develop and test key technologies for such reusable stages. The flight demonstrator ReFEx shall perform a controlled and autonomous re-entry from hypersonic velocity of approximately Mach 5 down to subsonic velocity after separation from the VSB-30 booster. The focus of this paper is the re-entry trajectory design for the ReFEx mission. Abbreviations AoA Angle of Attack AVS Avionics BC Ballistic Coefficient BoGC Begin of Guided Control CALLISTO Cooperative Action Leading to Launcher Innovation in Stage Tossback Operation DOF Degree of Freedom ELV Expendable Launch Vehicle EoE End Of Experiment GNC Guidance, Navigation and Control L/D Lift-to-Drag Ratio FPA Flight Path Angle LFBB Liquid Fly-Back Booster MECO Main Engine Cut-Off RCS Reaction Control System RLV Reusable Launch Vehicle TOSCA Trajectory Optimization and Simulation of Conventional and Advanced Spacecraft VTHL Vertical Takeoff, Horizontal Landing VTVL Vertical Takeoff, Vertical Landing 1. Introduction The recent successes of the emerging private space companies SpaceX and Blue Origin in landing, recovering and relaunching reusable first stages have demonstrated the possibility of building reliable and competitive reusable first stages. -
Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R
47th Lunar and Planetary Science Conference (2016) 1009.pdf Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R. M. Kelso2, R. Romo2, C. Andersen2 1 National Aeronautics & Space Administration (NASA), Kennedy Space Center (KSC), Swamp Works Labora- tory, ) Mail Stop: UB-R, KSC, Florida, 32899, PH (321)867-2557; email: [email protected] 2 Pacific International Space Center for Exploration System (PISCES), 99 Aupuni St, Hilo, HI 96720, PH (808)935-8270; email: [email protected], [email protected], [email protected]. Introduction: odologies for constructing infrastructure and facilities Recently, NASA Headquarters invited PISCES to on the Moon and Mars using in situ materials such as become a strategic partner in a new project called “Ad- planetary basalt material. By using the indigenous ditive Construction with Mobile Emplacement” regolith materials on extra-terrestrial bodies, then the (ACME). The goal of this project is to investigate high mass and corresponding high cost of transporting technologies and methodologies for constructing facili- construction materials (e.g. concrete) can be avoided. ties and surface systems infrastructure on the Moon and At approximately $10,000 per kg launched to Low Mars using planetary basalt material. The first phase of Earth Orbit (LEO) this is a significant cost savings this project is to robotically-build a 20 meter (65-ft) which will make the future expansion of human civili- diameter vertical takeoff, vertical landing (VTVL) zation into space more achievable. Part of the first pad out of local basalt material on the Big Island of phase of the ACME project is to robotically-build a 20 Hawaii. -
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE. -
L. Summerera,∗, A. Galvezb, D. Izzoa, F
64nd International Astronautical Congress, Beijing, China. Copyright 2013 by ESA. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-13.E.6.1.6 COMPETITIONS, GAMES AND PRIZES - MEANS FOR ADVANCED SPACE RESEARCH? L. Summerera,∗, A. Galvezb, D. Izzoa, F. Salzgeberc, A. de Clercqc, P. Manesc aESA Advanced Concepts Team, Keplerlaan 1, 2201 Noordwijk, The Netherlands bESA General Studies Programme, rue Mario Nikis, 75015 Paris, France cESA Technology Transfer Programme, Keplerlaan 1, 2201 Noordwijk, The Netherlands Abstract The traditional main mechanisms to advance science and technology in the space sector have recently been complemented by the use of competitions, prizes and games. Historically competitions and ex-ante prizes have played an important role among the tools of governments to stimulate innovation and advance science and technologies. Triggered by the success of the Ansari X-Prize in late 1990s / early 2000, these mechanisms have steadily gained grounds and supporters, also among governments. Scholarly literature on the effectiveness, advantages and disadvantages of these methods is emerging but still scarce. Most of the available scholarly literature assesses their impact based on US case studies and examples. The present paper provides a first analysis of these mechanisms and tools within the European Space Agency (ESA), based on three different areas: scientific research within its Advanced Concepts Team, business and innovation oriented competitions and prizes within the technology transfer programme and system level studies within the General Studies Programme. The ESA Advanced Concepts Team has experimented and used new ways of engaging with the larger scientific community via the use of scientific competitions, online games and scientific crowdsourcing experiments. -
Jacques Tiziou Space Collection
Jacques Tiziou Space Collection Isaac Middleton and Melissa A. N. Keiser 2019 National Air and Space Museum Archives 14390 Air & Space Museum Parkway Chantilly, VA 20151 [email protected] https://airandspace.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Administrative Information .............................................................................................. 1 Biographical / Historical.................................................................................................... 1 Scope and Contents........................................................................................................ 2 Arrangement..................................................................................................................... 2 Names and Subjects ...................................................................................................... 2 Container Listing ............................................................................................................. 4 Series : Files, (bulk 1960-2011)............................................................................... 4 Series : Photography, (bulk 1960-2011)................................................................. 25 Jacques Tiziou Space Collection NASM.2018.0078 Collection Overview Repository: National Air and Space Museum Archives Title: Jacques Tiziou Space Collection Identifier: NASM.2018.0078 Date: (bulk 1960s through -
Vertical Landing Aerodynamics of Reusable Rocket Vehicle
Trans. JSASS Aerospace Tech. Japan Vol. 10, pp. 1-4, 2012 Research Note Vertical Landing Aerodynamics of Reusable Rocket Vehicle 1) 2) 3) 1) 1) By Satoshi NONAKA, Hiroyuki NISHIDA, Hiroyuki KATO, Hiroyuki OGAWA and Yoshifumi INATANI 1) The Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Japan 2) Mechanical Systems Engineering, Tokyo University of Agriculture and Technology, Koganei, Japan 3) Chofu Aerospace Center, Japan Aerospace Exploration Agency, Chofu, Japan (Received November 26th, 2010) The aerodynamic characteristics of a vertical landing rocket are affected by its engine plume in the landing phase. The influences of interaction of the engine plume with the freestream around the vehicle on the aerodynamic characteristics are studied experimentally aiming to realize safe landing of the vertical landing rocket. The aerodynamic forces and surface pressure distributions are measured using a scaled model of a reusable rocket vehicle in low-speed wind tunnels. The flow field around the vehicle model is visualized using the particle image velocimetry (PIV) method. Results show that the aerodynamic characteristics, such as the drag force and pitching moment, are strongly affected by the change in the base pressure distributions and reattachment of a separation flow around the vehicle. Key Words: Counter Jet, Reusable Rocket, Landing Aerodynamics Nomenclature (VTVL) rocket vehicles are a type of reusable space transportation system. In the 1990s, the Delta Clipper 2 CD : drag coefficient, D (ρV∞ S 2) Experimental (DC-X) demonstrated both the key technical feasibility of a VTVL single stage to orbit (SSTO) vehicle 2 Cp : pressure coefficient, − ρ (Psurface P∞ ) ( V∞ S 2) and key operational concepts such as repeatability, safety, D : aerodynamic drag force [N] 1) reliability and inexpensive accessibility to space. -
Draft Environmental Assessment for Issuing an Experimental Permit to Spacex for Operation of the Grasshopper Vehicle at the Mcgregor Test Site, Texas September 2011
Federal Aviation Administration Draft Environmental Assessment for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas September 2011 HQ-111451 Draft EA for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas TABLE OF CONTENTS Section Page ACRONYMS AND ABBREVIATIONS ...................................................................................... iv 1. INTRODUCTION ....................................................................................................................1 1.1 Background .....................................................................................................................1 1.2 Purpose and Need for Agency Action .............................................................................2 1.3 Request for Comments on the Draft EA .........................................................................2 2. DESCRIPTION OF THE PROPOSED ACTION AND NO ACTION ALTERNATIVE ......3 2.1 Proposed Action ..............................................................................................................3 2.1.1 Grasshopper RLV ..............................................................................................5 2.1.1.1 Description ......................................................................................... 5 2.1.1.2 Pre-flight and Post-flight Activities ................................................... 5 2.1.1.3 Flight Profile (Takeoff, Flight, -
Corona Magazine #352 — Februar 2020
Corona Magazine #352 Februar 2020 Beschreibung & Impressum Das Corona Magazine ist ein traditionsreiches und nicht- kommerzielles Online-Projekt, das seit 1997 die Freunde von Science-Fiction, Phantastik, Wissenschaft, Kunst und guter Unterhaltung mit Informationen und Hintergründen, Analysen und Kommentaren versorgt. Seit dem Wechsel zum Verlag in Farbe und Bunt erscheint es im zeitgemäßen E-Book-Gewand. Redaktion Uwe Anton, Reiner Krauss, Bettina Petrik, Thorsten Walch, Reinhard Prahl, Alexandra Trinley, Oliver Koch, Lieven L. Litaer, Birgit Schwenger, Sven Wedekin, Kai Melhorn, Armin Rößler, Rüdiger Schäfer, Anna Pyzalski, C. R. Schmidt, Bernd Perplies, Hermann Ritter, Carsten Schmitt, Hartmut T. Klages, Frank Stein, Bastian Ludwig, Peter R. Krüger Herausgeber & Chefredakteur Der Verleger, Medienjournalist & Autor Björn Sülter schreibt Romane (Beyond Berlin, Ein Fall für die Patchwork Kids) & Sachbücher (Es lebe Star Trek, Die Star-Trek-Chro- nik), ist Headwriter und Experte für SYFY und mit Kolumnen und Artikeln bei Quotenmeter, Serienjunkies, in der GEEK! oder im FedCon Insider vertreten. Dazu präsentiert er seinen beliebten Podcast Planet Trek fm und ist als Hörbuchsprecher (Der Earl von Gaudibert, Dunkle Begegnungen, Star Trek - The Next Generation: Q 2 sind herzlich ausgeladen) und Moderator aktiv. Er lebt mit Frau, Tochter, Pferden, Hunden & Katze auf einem Bauern- hof irgendwo im Nirgendwo Schleswig-Holsteins. Ausgabe #352, Februar 2020 1. Auflage, 2020 ISBN 978-3-95936-201-6 © Februar 2020 / Alle Rechte vorbehalten in Farbe und Bunt Verlag Björn Sülter Am Bokholt 9 | 24251 Osdorf 3 www.ifub-verlag.de / www.ifubshop.com Herausgeber & Chefredakteur | Björn Sülter E-Book-Satz | EM Cedes & Reiner Krauss Lektorat | Bettina Petrik & Telma Vahey Cover | EM Cedes Cover-Fotos | Stephen Johnson & Guillaume de Germain auf Unsplash.com Foto von B. -
Aerospace America
June 2016 Ambition: Europa NASA might find more than life in this moon’s ocean. It could find a new strategy for exploring other worlds. Page 22 Oklahoma’s Bridenstine on climate, term limits/8 20 years of Design/Build/Fly/30 Smart bombs for wildfires/38 A PUBLICATION OF THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS • COVER-0616ƒ.indd 1 5/19/16 1:18 PM 2O16 13 –17 JUNE 2016 WASHINGTON, D.C. AIAA AVIATION 2016 is the only aviation Exclusive Premier Sponsor event that covers the entire integrated spectrum of aviation business and technology. Confirmed Speakers Charles F. Michimasa Maj. Gen. Mike Delaney John S. Richard A. Clarke Bolden Jr. Fujino Joe Engle Langford Vice President, Chairman & CEO, Administrator, President & CEO, United States Air Airplane Chairman and Good Harbor NASA Honda Aircraft Force (Ret.) Development, Chief Executive Security Risk Company The Boeing Officer, Aurora Management, LLC Company Flight Sciences Corporation REGISTER TODAY! AIAA-AVIATION.ORG 16-1132 June 2016 DEPARTMENTS Page 16 EDITOR’S NOTEBOOK 2 Congress’s dynamic aerospace duo IN BRIEF 4 3D-printed drone; status change at Ames? smart repair manuals; Page 34 subscale aircraft CONVERSATION 8 Change agent for aerospace CASE STUDY 12 Preventing more MH370s ENGINEERING NOTEBOOK 16 Making a money saver OUT OF THE PAST 46 Page 4 CAREER OPPORTUNITIES 48 FEATURES AMBITION: EUROPA 22 Jupiter’s moon Europa could have life in the ocean under its shell. NASA came up with a step-by-step plan to find out. Then, along came a congressman from Texas. by Debra Werner Page 38 DESIGNING A WINNER 30 AIAA’s Design/Build/Fly contest gives college students a chance to pit their engineering smarts against international competitors in a remote-controlled aircraft flyoff.